US11211184B2 - System of harness and engine case for aircraft engine - Google Patents
System of harness and engine case for aircraft engine Download PDFInfo
- Publication number
- US11211184B2 US11211184B2 US16/255,444 US201916255444A US11211184B2 US 11211184 B2 US11211184 B2 US 11211184B2 US 201916255444 A US201916255444 A US 201916255444A US 11211184 B2 US11211184 B2 US 11211184B2
- Authority
- US
- United States
- Prior art keywords
- aircraft engine
- metal shield
- engine according
- harness
- flange
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active, expires
Links
- 239000002184 metal Substances 0.000 claims abstract description 37
- 238000000926 separation method Methods 0.000 claims description 5
- 238000010292 electrical insulation Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 description 8
- 230000001681 protective effect Effects 0.000 description 7
- 239000004020 conductor Substances 0.000 description 6
- 239000000463 material Substances 0.000 description 4
- 239000003570 air Substances 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229920000642 polymer Polymers 0.000 description 2
- 239000004800 polyvinyl chloride Substances 0.000 description 2
- 229920000914 Metallic fiber Polymers 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 238000009954 braiding Methods 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 238000009429 electrical wiring Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B7/00—Insulated conductors or cables characterised by their form
- H01B7/17—Protection against damage caused by external factors, e.g. sheaths or armouring
- H01B7/18—Protection against damage caused by wear, mechanical force or pressure; Sheaths; Armouring
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B7/00—Insulated conductors or cables characterised by their form
- H01B7/0045—Cable-harnesses
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/28—Clamped connections, spring connections
- H01R4/30—Clamped connections, spring connections utilising a screw or nut clamping member
- H01R4/34—Conductive members located under head of screw
Definitions
- the application relates to electrical wire harnesses used in gas turbine engines, and to a grounding thereof.
- Electrical wire harness may be used in gas turbine engines to concurrently route a plurality of wires in a bundle from one location to another.
- Such electrical wire harnesses may have protective sheathes.
- outer braids may be used to protect the bundles of wires of a harness from the surrounding environment, and from chafing that may result from relative movement between the harness and surrounding engine components. The relative movement may be a result of thermal expansion, vibrations, etc.
- current may flow along electrical wire harnesses.
- an aircraft engine comprising: an engine case having at least one flange; a harness of wires extending in proximity to the engine case, the harness of wires including a metal shield sleeve externally covering a bundle of wires in a longitudinal direction, at least one break in the metal shield sleeve to provide at least two sleeve segments of the metal shield sleeve longitudinally spaced along the harness of wires; and a conductive contact between the at least one flange and at least one of the sleeve segments.
- an aircraft engine comprising: an engine case, the engine case having at least one flange; a harness of wires extending in proximity to the engine case, the harness of wires including at least two metal shield sleeves externally covering a bundle of wires in a longitudinal direction, the at least two metal shield sleeves being at least partially electrically insulated from one another; and a conductive contact between the at least one flange and at least one of the metal shield sleeve.
- FIG. 1 is a schematic longitudinal section view of a gas turbine engine using a system of harness and engine case in accordance with the present disclosure
- FIG. 2 is a schematic view of a system of harness and engine case in accordance with the present disclosure.
- FIG. 3 is a schematic view of a harness of the system of FIG. 2 .
- FIG. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a compressor section 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
- Components of the engine 10 are rotatable about a longitudinal center axis 11 of the engine 10 .
- Engine cases may be shown as 20 , including that of a gear box 19 .
- the present description uses an aircraft gas turbine for description purposes, the present description is applicable to any aircraft engine, including hybrid/electric engines, for example.
- an exemplary engine case 20 has case portions 21 .
- FIG. 2 shows four different case portions 21 , though fewer or more case portions 21 may be present.
- the case portions 21 may be known as shells, casings, etc.
- the case portions 21 may conventionally be made of a metallic material or alloys. In an embodiment, the case portions 21 may be made of other materials as well.
- the case portions 21 may be interconnected to one another by flanges 22 , or other such connection members.
- the flanges 22 may be a mated flange pair joining annular case sections 21 .
- the flanges 22 may be integral parts of the case portions 21 .
- a case portion 21 is cast with an end flange 22 .
- Case portions 21 may be sheet metal worked into the shells According to an embodiment shown in FIG. 3 , adjacent case portions 21 are connected to one another by abutment of end flanges 22 . Through holes 23 may be defined in the end flanges 22 . The through holes 23 may be in register for fasteners 24 to secure the case portions 21 together.
- the fasteners 24 may be bolts and nuts, as shown, but other fasteners include screws and other threaded fasteners, rivets, clamps, etc. This arrangement is one among others to fixedly secure case portions 21 together, with other arrangements including welding, brazing, etc.
- the harness 30 may be an electrical wiring harness that regroups a plurality of various wires serving different functions, tens of various wires.
- the wires are generically shown at 31 .
- Exemplary types of wires that may or may not be present in the harness 30 includes individual wires, twist singles (e.g., inner shielded twist singles), twisted pairs (e.g., shielded), and/or twisted triples/triplex (e.g., shielded), among others.
- Wires may be in various configurations, such as solid-core wires, stranded wires, multiconductor cables, type NM cables.
- Such wires may usually include a conductor wire (e.g., a metallic wire) with an insulating sheath, wire armouring, bedding, insulation, separation material and/or sleeve (e.g., a rubber or polymer such as polyvinyl chloride (PVC)).
- a conductor wire e.g., a metallic wire
- an insulating sheath e.g., a insulating sheath, wire armouring, bedding, insulation, separation material and/or sleeve
- sleeve e.g., a rubber or polymer such as polyvinyl chloride (PVC)
- the harness 30 may further have a flexible metal shield sleeve or sheath surrounding and enclosing the bundle of wires 31 .
- the flexible metal shield sleeve 32 may for instance be an outer overbraid 32 (a.k.a, outer braid, shielding braid, metallic braid).
- the braid 32 may be composed of threads woven tightly around the bundle of wires 31 .
- the braid 32 includes threads of metal, and is therefore conductive.
- the braid 32 may result from spindle type braiding machine.
- the overbraid 32 provides a protective layer for the bundle of wires 31 , for example to protect the bundle of wires 31 from chafing, heat and/or other wear and tear.
- the braid 32 or like metal shield sleeve is generally not rigid or flexible, to allow some flexibility in routing the harness 30 from one engine location to another.
- the harness 30 may further have a protective insulating sheath 33 covering the flexible metal shield sleeve 32 .
- the optional protective insulating sheath 33 may be a rubber or polymer such as polyvinyl chloride (PVC), as examples.
- PVC polyvinyl chloride
- the protective insulating sheath 33 is a tape wound onto the sleeve 32 .
- One or more breaks 34 are defined in the metal shield sleeve 32 , such that the metal shield sleeve is formed of two or more separate segments, shown as 32 A, 32 B, etc.
- the outer over braid 32 has three breaks 34 along the length of the harness 30 .
- the segments may also be regarded as distinct metal shield sleeves 32 A, 32 B, 32 C separated from one another by the breaks 34 .
- Such distinct metal shield sleeves 32 A, 32 B, 32 C may hence cover different longitudinal portions of the bundle of wires 31 , with no overlap and/or contact between the distinct metal shield sleeves 32 A, 32 B, 32 C.
- the breaks 34 may also be known as discontinuities in the metal shield sleeve 32 , as the sleeve 32 is not continuous along the length of the harness 30 .
- the discontinuities are conductive discontinuities, as current may not be conducted along the sleeve 32 due to the break 34 .
- the breaks 34 in the harness 30 are of at least 0.2 inch.
- the breaks 34 are between 0.3 to 0.5 inch. If the protective insulating sheath 33 is present, it may or may not have a break(s) generally aligned with the break(s) 34 . In an embodiment, the protective insulating sheath 33 is continuous, but is pierced for the sleeve 32 to be exposed and/or for a conductor wire to pass through the sheath 33 .
- the shields 32 are grounded to the engine case 20 , by way of a conductive contact, at bonding points.
- the conductive contact may be in the form of a conductor wire 35 (a.k.a., strap, bond strap) whose conducting portion is conductively connected to one of the shield segments (e.g., 32 A, 32 B, etc) at one end, and to a flange 22 of the engine case 20 at another end.
- the conductor wire 35 may have an insulating sleeve.
- the conductor wire 35 may have appropriate connectors to be connected at its opposed ends.
- the conductor wire 35 may have a terminal lug 36 or bracket to be retained by the fastener 24 as shown in FIG. 3 .
- the conductive contact may be in the form of a direct conductive contact between the material of the sleeve 32 and that of the flanges 22 .
- the conductive contact may be in the form of a direct conductive contact between the material of the sleeve 32 with that of metallic stand-off bracket conductively connected to the flange 22 .
- the harness 30 extends in close proximity to the engine case 20 .
- the harness 30 extends along the engine case 20 .
- the harness 30 may extend lengthwise concurrently with the engine case 20 .
- the length of the harness 30 may also be transverse to the engine case 20 .
- the harness 30 may be coupled to connectors 41 in a firewall 40 of the gas turbine engine.
- the harness 30 may be fabricated, assembled and/or altered for the breaks 34 or for exposed portions of the sleeve 32 to be at locations corresponding to the location of the flanges 22 on the engine case 20 and/or accessory mounting bolt and brackets 24 that are conductive through a bolt.
- the conductive contact between the segments of the sleeve 32 , e.g., at the breaks 34 , and additional grounding points aid in diverting current away from the harness 30 onto the engine structure and into engine bond straps 42 and mounts ( FIG. 2 ).
- the configuration described with reference to FIGS. 2 and 3 with the locations of the bonding points aligned with the flanges 22 of the engine case portions 21 may facilitate the installation of grounding for the harness 30 .
- minimal additional hardware may be required to benefit from the advantages of bonding of the harness 30 .
- the breaks 34 in the shielding 32 and the ground points promote the current to take the larger skin of the engine diameter, e.g., that of an engine case 20 , rather the smaller diameter harness 30 .
- Current traveling along the outer shield 32 of the harness 30 may be forced onto the engine structure through conductive contact 35 , and may then tend to remain on the engine structure rather than return back onto the harness 30 through another conductive contact 35 due to the reduced impedance of the larger engine component.
- conductive contact 35 is at one of the breaks 34 , and is located aft of the engine mount and engine bond straps to promote the current conducting along the skin of the engine and engine to aircraft bond straps 42 rather than being conducting back onto the harness 30 through conductive wires 35 .
- the grounding or bonding arrangement for the harness 30 described above may also be used for other structural components of the gas turbine engine 10 , i.e., not necessarily an engine case 20 .
- the approach is applicable to any aircraft engine type, and not uniquely applicable to gas turbine engines.
- a definition that may be used for the break 34 is an annular gap between two adjacent sleeves 32 , sleeve segments of the sleeve 32 , the annular gap surrounding the harness (as do the sleeves 32 /sleeve segments).
- the annular gap forms an annular discontinuity in the sleeve 32 for example, resulting in a drop of conductivity.
- This may be referred to as the two metal shield sleeves 32 being at least partially electrically insulated from one another, i.e., there is at least a drop of conductivity.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
- Insulated Conductors (AREA)
Abstract
Description
Claims (20)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US16/255,444 US11211184B2 (en) | 2019-01-23 | 2019-01-23 | System of harness and engine case for aircraft engine |
CA3069191A CA3069191A1 (en) | 2019-01-23 | 2020-01-21 | System of harness and engine case for aircraft engine |
EP20153123.3A EP3686412B1 (en) | 2019-01-23 | 2020-01-22 | System of harness and engine case for aircraft engine |
PL20153123.3T PL3686412T3 (en) | 2019-01-23 | 2020-01-22 | System of harness and engine case for aircraft engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US16/255,444 US11211184B2 (en) | 2019-01-23 | 2019-01-23 | System of harness and engine case for aircraft engine |
Publications (2)
Publication Number | Publication Date |
---|---|
US20200234849A1 US20200234849A1 (en) | 2020-07-23 |
US11211184B2 true US11211184B2 (en) | 2021-12-28 |
Family
ID=69570506
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US16/255,444 Active 2040-03-09 US11211184B2 (en) | 2019-01-23 | 2019-01-23 | System of harness and engine case for aircraft engine |
Country Status (4)
Country | Link |
---|---|
US (1) | US11211184B2 (en) |
EP (1) | EP3686412B1 (en) |
CA (1) | CA3069191A1 (en) |
PL (1) | PL3686412T3 (en) |
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Also Published As
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US20200234849A1 (en) | 2020-07-23 |
EP3686412B1 (en) | 2023-05-10 |
EP3686412A1 (en) | 2020-07-29 |
PL3686412T3 (en) | 2023-09-04 |
CA3069191A1 (en) | 2020-07-23 |
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